A hydraulic actuator system 1 is provided for driving a movable portion attached to a wing 5 of an airplane. A plurality of first system hydraulic actuators 2 and a plurality of second system hydraulic actuators 3 are included and are connected to the movable portion. The first system hydraulic actuators 2 are attached to the wing 5 and connected to a first hydraulic pressure source, whereas the second system hydraulic actuators 3 are attached to the wing to be in parallel to the first system hydraulic actuators 2 and are connected to a second hydraulic pressure source. The first system hydraulic actuators 2 and the second system hydraulic actuators 3 are alternately provided at a predetermined part of the wing 5.
Hydraulic actuator system for aircraft
Hydraulisches Aktuatorsystem für Flugzeuge
Système d'actionneur hydraulique pour aéronefs
2017-08-23
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |